Aircraft engine nacelle assembly tool

Abstract

The utility model relates to the field of aircraft part assembling, and particularly discloses an aircraft engine nacelle assembling tool which is used for assembling an aircraft engine nacelle, and a connector positioning mechanism is arranged at the upper end of a tool support and used for positioning an installation section connector. The front edge beam positioning mechanism is arranged at the upper end of the tool support and used for positioning a front edge I-shaped beam of the engine nacelle. The reinforcing box positioning mechanism is arranged at the upper end of the tool support and used for positioning and supporting a reinforcing box of the engine nacelle. The lifting point supporting box positioning mechanism is arranged at the upper end of the tool support. The trailing edge beam positioning mechanism is arranged at the upper end of the tool support and used for positioning a trailing edge beam of the engine nacelle. The rib plate positioning mechanism is arranged at the upper end of the tool bracket; the skin positioning mechanism is arranged at the upper end of the tool support and used for positioning and supporting the skin of the engine nacelle. According to the utility model, the part does not deform, the position of the part can be accurately positioned, and the assembly precision and efficiency are improved.

Description

Technical Field

[0001] The utility model relates to the field of aircraft part assembly, and particularly to an assembly tool for an aircraft engine nacelle. Background Art

[0002] An aircraft engine nacelle is a compartment on an aircraft where the engine is placed. It needs to have a good aerodynamic shape to reduce flight resistance, and at the same time, it also needs to have the ability to prevent and remove ice, protect the engine from being disturbed and work properly, and facilitate the maintenance and repair of the engine on the ground. The aircraft engine nacelle is an integrated system with extremely high technical difficulty, and its development, production, and supply all require many years of experience. Due to the complex structure of the aircraft engine nacelle, involving a variety of materials and precise designs, most of the existing assembly tools are complex in structure, high in cost, and complex in maintenance. In addition, there are also problems such as slow assembly work and inaccurate assembly. In view of the above existing problems, it is very necessary to research and design a new type of aircraft engine nacelle assembly tool to overcome the problems existing in the existing aircraft engine nacelle assembly. Summary of the Invention

[0003] In order to solve the problems of low work efficiency and inaccurate assembly existing in the existing aircraft engine nacelle assembly, the utility model provides an assembly tool for an aircraft engine nacelle.

[0004] The technical solution adopted by the utility model to achieve the above purpose is: an assembly tool for an aircraft engine nacelle, used for assembling an aircraft engine nacelle, including a tooling bracket, a joint positioning mechanism, a leading edge beam positioning mechanism, a lifting point support box positioning mechanism, a strengthening box positioning mechanism, a trailing edge beam positioning mechanism, a rib plate positioning mechanism, and a skin positioning mechanism; the joint positioning mechanism is arranged at the upper end of the tooling bracket and is used for positioning the aircraft engine mounting joint; the leading edge beam positioning mechanism is arranged at the upper end of the tooling bracket and is used for positioning the leading edge I-beam of the engine nacelle; the strengthening box positioning mechanism is arranged at the upper end of the tooling bracket and is used for positioning and supporting the strengthening box of the engine nacelle; the lifting point support box positioning mechanism is arranged at the upper end of the tooling bracket and is used for positioning and supporting the lifting point support box of the engine and positioning the lifting point connecting piece of the engine; the trailing edge beam positioning mechanism is arranged at the upper end of the tooling bracket and is used for positioning the trailing edge beam of the engine nacelle; the rib plate positioning mechanism is arranged at the upper end of the tooling bracket and is used for positioning the rib plate of the engine nacelle; the skin positioning mechanism is arranged at the upper end of the tooling bracket and is used for positioning and supporting the skin of the engine nacelle.

[0005] According to some embodiments of the present application, an aircraft engine nacelle assembly tool, the joint positioning mechanism includes two joint positioning components, the two joint positioning components are respectively arranged on the left and right sides of the upper front end of the tooling bracket, the joint positioning component includes a joint support plate and a joint positioning plate connected to each other, the joint support plate is an L-shaped plate, the horizontal portion of the joint support plate is connected to the tooling bracket, the vertical portion of the joint support plate is connected to the joint positioning plate by a pin, the joint positioning plate is provided with a joint positioning hole, the installation joint is provided with a joint limiting hole, the positioning bolt passes through the joint positioning hole and the joint limiting hole, the nut is screwed on the positioning bolt to fix the installation joint to the joint positioning plate.

[0006] According to an aircraft engine nacelle assembly tool in some embodiments of the present application, the leading edge beam positioning mechanism includes a leading edge beam middle positioning assembly and two leading edge beam end positioning assemblies;

[0007] The front edge beam middle positioning assembly is arranged at the middle position of the front side of the upper end of the tooling bracket, and the front edge beam middle positioning assembly comprises a front edge beam middle support plate and a front edge beam middle positioning plate connected to each other, the front edge beam middle support plate is an L-shaped plate, the horizontal portion of the front edge beam middle support plate is connected to the tooling bracket, the vertical portion of the front edge beam middle support plate is connected to the front edge beam middle positioning plate through a latch, the front edge beam middle positioning plate is provided with a front edge beam middle positioning hole, the front edge I-beam is provided with a front edge beam middle limiting hole, the positioning bolt passes through the front edge beam middle positioning hole and the front edge beam middle limiting hole, and the nut is screwed on the positioning bolt to fix the front edge I-beam on the front edge beam middle positioning plate;

[0008] The two leading edge beam end positioning assemblies are respectively arranged on the left and right sides of the upper end of the tooling bracket, and are arranged on the inner side of the skin positioning mechanism, the leading edge beam end positioning assembly includes a leading edge beam end support plate and a leading edge beam end positioning plate connected to each other, the leading edge beam end support plate is an L-shaped plate, the horizontal part of the leading edge beam end support plate is connected to the tooling bracket, the vertical part of the leading edge beam end support plate is connected to the leading edge beam end positioning plate through a pin, the leading edge beam end positioning plate is provided with a leading edge beam end positioning hole, the leading edge I-beam is provided with a leading edge beam end limiting hole, the positioning bolt passes through the leading edge beam end positioning hole and the leading edge beam end limiting hole, the nut is screwed on the positioning bolt to fix the leading edge I-beam on the leading edge beam end positioning plate.

[0009] An aircraft engine nacelle assembly tooling according to some embodiments of the present application. The stiffening box positioning mechanism is arranged between the two leading edge beam end positioning components. The stiffening box positioning mechanism includes two stiffening box support plates and a stiffening box positioning plate. The two stiffening box support plates are respectively arranged on the left and right sides below the stiffening box positioning plate. The stiffening box support plate is an L-shaped plate. The horizontal part of the stiffening box support plate is connected to the tooling bracket, and the vertical part of the stiffening box support plate is connected to the stiffening box positioning plate. The stiffening box positioning plate is provided with a stiffening box positioning hole, and the stiffening box is provided with a stiffening box limiting hole. A positioning bolt passes through the stiffening box positioning hole and the stiffening box limiting hole, and a nut is screwed onto the positioning bolt to fix the upper stiffening box on the stiffening box positioning plate.

[0010] An aircraft engine nacelle assembly tooling according to some embodiments of the present application. The upper surface of the stiffening box positioning plate is an inclined surface that fits the lower surface of the stiffening box.

[0011] An aircraft engine nacelle assembly tooling according to some embodiments of the present application. The suspension point support box positioning mechanism includes two suspension point support box positioning components. The two suspension point support box positioning components are respectively arranged on the left and right sides of the middle part of the upper end of the tooling bracket and are arranged inside the skin positioning mechanism. The suspension point support box positioning component includes a suspension point support box support plate and a suspension point support box positioning plate that are connected to each other. The suspension point support box support plate is an L-shaped plate. The horizontal part of the suspension point support box support plate is connected to the tooling bracket, and the vertical part of the suspension point support box support plate is connected to the suspension point support box positioning plate. The suspension point support box positioning plate is provided with a suspension point support box positioning hole and a connector positioning hole. The suspension point support box is provided with a suspension point support box limiting hole. A positioning bolt passes through the suspension point support box positioning hole and the suspension point support box limiting hole, and a nut is screwed onto the positioning bolt to fix the suspension point support box on the suspension point support box positioning plate. The suspension point connector is provided with a connector limiting hole. A positioning bolt passes through the connector positioning hole and the connector limiting hole, and a nut is screwed onto the positioning bolt to fix the suspension point connector on the suspension point support box positioning plate.

[0012] An aircraft engine nacelle assembly tooling according to some embodiments of the present application. The upper surface of the suspension point support box positioning plate is an inclined surface that fits the suspension point support box.

[0013] An aircraft engine nacelle assembly tooling according to some embodiments of the present application. The trailing edge beam positioning mechanism includes two trailing edge beam positioning components, which are respectively arranged on the left and right sides of the rear part of the upper end of the tooling bracket and inside the skin positioning mechanism. The trailing edge beam positioning component includes a trailing edge beam support plate and a trailing edge beam positioning plate connected to each other. The trailing edge beam support plate is an L-shaped plate. The horizontal part of the trailing edge beam support plate is connected to the tooling bracket, and the vertical part of the trailing edge beam support plate is connected to the trailing edge beam positioning plate. The trailing edge beam positioning plate is provided with a trailing edge beam positioning hole, and the trailing edge beam is provided with a trailing edge beam limiting hole. A positioning bolt passes through the trailing edge beam positioning hole and the trailing edge beam limiting hole, and a nut is screwed onto the positioning bolt to fix the trailing edge beam on the trailing edge beam positioning plate.

[0014] An aircraft engine nacelle assembly tooling according to some embodiments of the present application. The rib plate positioning mechanism includes four rib plate positioning components, which are respectively arranged on the left and right sides of the upper end of the tooling bracket. The rib plate positioning component includes a rib plate support plate and a rib plate positioning plate. The rib plate support plate is an L-shaped plate. The horizontal part of the rib plate support plate is connected to the tooling bracket, and the vertical part of the rib plate support plate is connected to the rib plate positioning plate through a pin. The rib plate positioning plate is provided with a rib plate positioning hole, and the rib plate is provided with a rib plate limiting hole. A positioning bolt passes through the rib plate positioning hole and the rib plate limiting hole, and a nut is screwed onto the positioning bolt to fix the rib plate on the rib plate positioning plate.

[0015] An aircraft engine nacelle assembly tooling according to some embodiments of the present application. The skin positioning mechanism includes two skin positioning plates, which are respectively arranged on the left and right sides of the upper end of the tooling bracket. The left and right ends of the skin positioning plate are respectively connected to the rib plate positioning plate, and the upper surface of the skin positioning plate is an arc surface that fits the bottom of the skin.

[0016] The aircraft engine nacelle assembly tooling of the present utility model has a simple structure and a short installation time of the tooling. It is positioned and installed in the form of limiting holes, positioning holes, positioning bolts and nuts, and can assemble the aircraft engine nacelle without deforming the parts of the aircraft engine nacelle. Moreover, it can accurately position the positions of the parts during the assembly process, not only reducing the error of manual positioning but also improving the assembly accuracy and assembly efficiency. Description of the Drawings

[0017] Figure 1 is the overall structural schematic diagram of the aircraft engine nacelle assembly tooling in the embodiment of the present utility model;

[0018] Figure 2 is the overall structural schematic diagram of the aircraft engine nacelle after positioning in the embodiment of the present utility model;

[0019] Figure 3 It is a schematic structural diagram of the connection between the positioning mechanism of the reinforcement box and the reinforcement box in the embodiment of the present utility model;

[0020] Figure 4 It is a schematic structural diagram of the connection between the positioning mechanism of the suspension point support box, the suspension point support box and the suspension point connecting piece in the embodiment of the present utility model.

[0021] In the figure: 1. Tooling support bracket, 2. Joint support plate, 3. Joint positioning plate, 4. Middle support plate of leading edge beam, 5. Middle positioning plate of leading edge beam, 6. End support plate of leading edge beam, 7. End positioning plate of leading edge beam, 8. Support plate of suspension point support box, 9. Positioning plate of suspension point support box, 10. Support plate of reinforcement box, 11. Positioning plate of reinforcement box, 12. Support plate of trailing edge beam, 13. Positioning plate of trailing edge beam, 14. Support plate of rib, 15. Positioning plate of rib, 16. Skin positioning plate, 17. Installation joint, 18. Suspension point support box, 19. Suspension point connecting piece, 20. Reinforcement box, 21. Rib, 22. Skin. Specific embodiments

[0022] The following further describes in detail the embodiments of the present utility model in conjunction with the drawings and embodiments. The following embodiments are used to illustrate the present utility model, but cannot be used to limit the scope of the present utility model.

[0023] In the description of the present utility model, it should be noted that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the present utility model. The terms "installation", "connection" and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the internal communication of two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances. In addition, in the description of the present utility model, unless otherwise specified, the meaning of "a plurality" is two or more.

[0024] A kind of aircraft engine nacelle assembly tooling in this embodiment, as Figure 1 and Figure 2As shown, it is used for assembling an aircraft engine nacelle, including a tooling bracket 1, a joint positioning mechanism, a leading edge beam positioning mechanism, a suspension point support box positioning mechanism, a reinforcement box positioning mechanism, a trailing edge beam positioning mechanism, a rib plate positioning mechanism, and a skin positioning mechanism; the joint positioning mechanism is arranged at the upper end of the tooling bracket 1 and is used for positioning the aircraft engine mounting joint 17; the leading edge beam positioning mechanism is arranged at the upper end of the tooling bracket 1 and is used for positioning the leading edge I-beam of the engine nacelle; the reinforcement box positioning mechanism is arranged at the upper end of the tooling bracket 1 and is used for positioning and supporting the reinforcement box 20 of the engine nacelle; the suspension point support box positioning mechanism is arranged at the upper end of the tooling bracket 1 and is used for positioning and supporting the suspension point support box 18 of the engine and positioning the suspension point connecting piece 19 of the engine; the trailing edge beam positioning mechanism is arranged at the upper end of the tooling bracket 1 and is used for positioning the trailing edge beam of the engine nacelle; the rib plate positioning mechanism is arranged at the upper end of the tooling bracket 1 and is used for positioning the rib plate 21 of the engine nacelle; the skin positioning mechanism is arranged at the upper end of the tooling bracket 1 and is used for positioning and supporting the skin 22 of the engine nacelle.

[0025] The joint positioning mechanism includes two joint positioning components, which are respectively arranged on the left and right sides of the front part of the upper end of the tooling bracket 1. The joint positioning component includes a joint support plate 2 and a joint positioning plate 3 which are connected to each other. The joint support plate 2 is an L-shaped plate. The horizontal part of the joint support plate 2 is connected to the tooling bracket 1, and the vertical part of the joint support plate 2 is connected to the joint positioning plate 3 through a pin. There is a through hole on the upper side of the vertical part of the joint support plate 2, and there is a through hole at the corresponding position on the lower side of the joint positioning plate 3 and the upper side of the vertical part of the joint support plate 2. The pin passes through the through hole on the upper side of the vertical part of the joint support plate 2 and the through hole on the lower side of the joint positioning plate 3 to connect the vertical part of the joint support plate 2 and the joint positioning plate 3. The connection through the pin can make the disassembly between the vertical part of the joint support plate 2 and the joint positioning plate 3 more convenient and fast. It is not only convenient for the operator to operate, but also saves the installation time of the tooling, and can effectively improve the tooling installation efficiency and the working efficiency when assembling the aircraft engine nacelle. The joint positioning plate 3 is provided with a plurality of joint positioning holes, and the mounting joint 17 is provided with a plurality of joint limit holes. The positioning bolt passes through the corresponding joint positioning hole and the joint limit hole, and the nut is screwed on the positioning bolt to fix the mounting joint 17 on the joint positioning plate 3. As a preference of this embodiment, four joint positioning holes are provided on each joint positioning plate 3. Fixing the mounting joint 17 and the joint positioning plate 3 by means of the joint positioning holes, joint limit holes, positioning bolts and nuts is not only convenient for disassembly, but also can freely adjust the clamping force, and will not cause deformation of the mounting joint 17 and the joint positioning plate 3.

[0026] The leading edge beam positioning mechanism includes a leading edge beam middle positioning component and two leading edge beam end positioning components; the leading edge beam middle positioning component is arranged at the middle position on the front side of the upper end of the tooling bracket 1. The leading edge beam middle positioning component includes a leading edge beam middle support plate 4 and a leading edge beam middle positioning plate 5 which are connected to each other. The leading edge beam middle support plate 4 is an L-shaped plate. The horizontal part of the leading edge beam middle support plate 4 is connected to the tooling bracket 1, and the vertical part of the leading edge beam middle support plate 4 is connected to the leading edge beam middle positioning plate 5 through a pin. There is a through hole on the upper side of the vertical part of the leading edge beam middle support plate 4, and there is a through hole at the corresponding position on the lower side of the leading edge beam middle positioning plate 5 corresponding to the through hole on the upper side of the vertical part of the leading edge beam middle support plate 4. The pin passes through the through hole on the upper side of the vertical part of the leading edge beam middle support plate 4 and the through hole on the lower side of the leading edge beam middle positioning plate 5 to connect the vertical part of the leading edge beam middle support plate 4 and the leading edge beam middle positioning plate 5. The connection through the pin can make the disassembly between the vertical part of the leading edge beam middle support plate 4 and the leading edge beam middle positioning plate 5 more convenient and fast, facilitating the operation of the operator, saving the installation time of the tooling, improving the tooling installation efficiency and the working efficiency when assembling the aircraft engine nacelle. The leading edge beam middle positioning plate 5 is provided with a leading edge beam middle positioning hole, and the leading edge I-beam is provided with a leading edge beam middle limiting hole. The positioning bolt passes through the leading edge beam middle positioning hole and the leading edge beam middle limiting hole, and the nut is screwed onto the positioning bolt to fix the leading edge I-beam on the leading edge beam middle positioning plate 5; the two leading edge beam end positioning components are respectively arranged on the left and right sides of the upper end of the tooling bracket 1 and are arranged inside the skin positioning mechanism. The leading edge beam end positioning component includes a leading edge beam end support plate 6 and a leading edge beam end positioning plate 7 which are connected to each other. The leading edge beam end support plate 6 is an L-shaped plate. The horizontal part of the leading edge beam end support plate 6 is connected to the tooling bracket 1, and the vertical part of the leading edge beam end support plate 6 is connected to the leading edge beam end positioning plate 7 through a pin. There is a through hole on the upper side of the vertical part of the leading edge beam end support plate 6, and there is a through hole at the corresponding position on the lower side of the leading edge beam end positioning plate 7 corresponding to the through hole on the upper side of the vertical part of the leading edge beam end support plate 6. The pin passes through the through hole on the upper side of the vertical part of the leading edge beam end support plate 6 and the through hole on the lower side of the leading edge beam end positioning plate 7 to connect the vertical part of the leading edge beam end support plate 6 and the leading edge beam end positioning plate 7. The connection through the pin can make the disassembly between the vertical part of the leading edge beam end support plate 6 and the leading edge beam end positioning plate 7 more convenient and fast. The leading edge beam end positioning plate 7 is provided with a leading edge beam end positioning hole, and the leading edge I-beam is provided with a leading edge beam end limiting hole. The positioning bolt passes through the leading edge beam end positioning hole and the leading edge beam end limiting hole, and the nut is screwed onto the positioning bolt to fix the leading edge I-beam on the leading edge beam end positioning plate 7.

[0027] Such as Figure 3As shown in the figure, the reinforcing box positioning mechanism is arranged between the positioning components at the two ends of the front edge beam. The reinforcing box positioning mechanism includes two reinforcing box support plates 10 and a reinforcing box positioning plate 11. The two reinforcing box support plates 10 are respectively arranged on the left and right sides below the reinforcing box positioning plate 11. The reinforcing box support plate 10 is an L-shaped plate. The horizontal part of the reinforcing box support plate 10 is connected to the tooling bracket 1, and the vertical part of the reinforcing box support plate 10 is connected to the reinforcing box positioning plate 11. The reinforcing box positioning plate 11 is provided with a plurality of reinforcing box positioning holes, and the reinforcing box 20 is provided with a plurality of reinforcing box limiting holes. The positioning bolts pass through the corresponding reinforcing box positioning holes and reinforcing box limiting holes, and the nuts are screwed onto the positioning bolts to fix the upper reinforcing box 20 on the reinforcing box positioning plate 11. As a preference of this embodiment, four reinforcing box positioning holes are provided on each reinforcing box positioning plate 11. Fixing the reinforcing box 20 and the reinforcing box positioning plate 11 by means of the reinforcing box positioning holes, reinforcing box limiting holes, positioning bolts and nuts is not only convenient for disassembly, but also can freely adjust the clamping force, and will not cause deformation of the reinforcing box 20 and the reinforcing box positioning plate 11. The upper surface of the reinforcing box positioning plate 11 is an inclined surface that fits the lower surface of the reinforcing box 20. By setting the inclined surface, deformation of the lower surface of the reinforcing box 20 can be prevented.

[0028] As Figure 4 shown in the figure, the suspension point support box positioning mechanism includes two suspension point support box positioning components. The two suspension point support box positioning components are respectively arranged on the left and right sides of the middle part of the upper end of the tooling bracket 1 and are arranged inside the skin positioning mechanism. The suspension point support box positioning component includes a suspension point support box support plate 8 and a suspension point support box positioning plate 9 that are connected to each other. The suspension point support box support plate 8 is an L-shaped plate. The horizontal part of the suspension point support box support plate 8 is connected to the tooling bracket 1, and the vertical part of the suspension point support box support plate 8 is connected to the suspension point support box positioning plate 9. The suspension point support box positioning plate 9 is provided with a suspension point support box positioning hole and a connector positioning hole. The suspension point support box 18 is provided with a suspension point support box limiting hole. The positioning bolts pass through the suspension point support box positioning hole and the suspension point support box limiting hole, and the nuts are screwed onto the positioning bolts to fix the suspension point support box 18 on the suspension point support box positioning plate 9. The suspension point connector 19 is provided with a connector limiting hole. The positioning bolts pass through the connector positioning hole and the connector limiting hole, and the nuts are screwed onto the positioning bolts to fix the suspension point connector 19 on the suspension point support box positioning plate 9. Fixing the suspension point support box 18 and the suspension point support box positioning plate 9 and fixing the suspension point connector 19 and the suspension point support box positioning plate 9 by means of the positioning bolts and nuts is not only convenient for disassembly, but also can freely adjust the clamping force, and will not cause deformation of the suspension point support box 18, the suspension point support box positioning plate 9 and the suspension point connector 19. The upper surface of the suspension point support box positioning plate 9 is an inclined surface that fits the suspension point support box 18, which can prevent deformation of the lower surface of the suspension point support box 18.

[0029] The trailing edge beam positioning mechanism includes two trailing edge beam positioning components, which are respectively arranged on the left and right sides of the rear part of the upper end of the tooling bracket 1 and inside the skin positioning mechanism. The trailing edge beam positioning component includes a trailing edge beam support plate 12 and a trailing edge beam positioning plate 13 that are connected to each other. The trailing edge beam support plate 12 is an L-shaped plate. The horizontal part of the trailing edge beam support plate 12 is connected to the tooling bracket 1, and the vertical part of the trailing edge beam support plate 12 is connected to the trailing edge beam positioning plate 13. The vertical part of the trailing edge beam support plate 12 and the trailing edge beam positioning plate 13 can be connected by a pin. There is a through hole on the upper side of the vertical part of the trailing edge beam support plate 12, and a through hole is provided at the corresponding position of the lower side of the trailing edge beam positioning plate 13 and the upper side of the vertical part of the trailing edge beam support plate 12. The pin passes through the through hole on the upper side of the vertical part of the trailing edge beam support plate 12 and the through hole on the lower side of the trailing edge beam positioning plate 13 to connect the vertical part of the trailing edge beam support plate 12 and the trailing edge beam positioning plate 13. The connection by the pin can make the disassembly between the vertical part of the trailing edge beam support plate 12 and the trailing edge beam positioning plate 13 more convenient and fast, saving the installation time of the tooling. The trailing edge beam positioning plate 13 is provided with a plurality of trailing edge beam positioning holes, and the trailing edge beam is provided with a plurality of trailing edge beam limiting holes. The positioning bolt passes through the trailing edge beam positioning hole and the trailing edge beam limiting hole, and the nut is screwed onto the positioning bolt to fix the trailing edge beam on the trailing edge beam positioning plate 13. As a preference of this embodiment, one trailing edge beam positioning hole is opened on each of the upper and lower sides of each trailing edge beam positioning plate 13, and two trailing edge beam limiting holes are opened at two diagonal corners of the trailing edge beam. During actual use, only by fixing two places, the trailing edge beam can be fixed on the trailing edge beam positioning mechanism, which can improve the working efficiency of the installation of the aircraft engine nacelle. In addition, by fixing the trailing edge beam and the trailing edge beam positioning plate 13 through the trailing edge beam positioning holes, the trailing edge beam limiting holes, the positioning bolts and the nuts, it is not only convenient for disassembly, but also the clamping force can be freely adjusted, and the trailing edge beam and the trailing edge beam positioning plate 13 will not be deformed.

[0030] The rib positioning mechanism includes four rib positioning components, which are respectively arranged on the left and right sides of the upper end of the tooling bracket 1. The rib positioning component includes a rib support plate 14 and a rib positioning plate 15. The rib support plate 14 is an L-shaped plate. The horizontal part of the rib support plate 14 is connected to the tooling bracket 1, and the vertical part of the rib support plate 14 is connected to the rib positioning plate 15 by a pin. The rib positioning plate 15 is provided with rib positioning holes, and the rib 21 is provided with rib limiting holes. The positioning bolt passes through the rib positioning hole and the rib limiting hole, and the nut is screwed onto the positioning bolt to fix the rib 21 on the rib positioning plate 15.

[0031] The skin positioning mechanism includes two skin positioning plates 16, which are respectively arranged on the left and right sides of the upper end of the tooling bracket 1. The left and right ends of the skin positioning plates 16 are respectively connected to the rib plate positioning plates 15. The upper surface of the skin positioning plates 16 is an arc surface that fits the bottom of the skin 22, which can effectively prevent the lower edge of the skin 22 from deforming due to gravity and causing damage to the parts, and can better position the skin 22.

[0032] The embodiments of the present invention are given for purposes of illustration and description, and are not exhaustive or limit the present invention to the disclosed form. Many modifications and variations are obvious to those of ordinary skill in the art. The embodiments are selected and described to better illustrate the principles and practical applications of the present invention, and to enable those of ordinary skill in the art to understand the present invention and thus design various embodiments with various modifications suitable for specific purposes.

Claims

1. An aircraft engine nacelle assembly tooling for assembling an aircraft engine nacelle, characterized in that, It includes a tooling support bracket (1), a joint positioning mechanism, a leading edge beam positioning mechanism, a suspension point support box positioning mechanism, a reinforcement box positioning mechanism, a trailing edge beam positioning mechanism, a rib plate positioning mechanism, and a skin positioning mechanism; the joint positioning mechanism is arranged at the upper end of the tooling support bracket (1) and is used for positioning the aircraft engine mounting joint (17); the leading edge beam positioning mechanism is arranged at the upper end of the tooling support bracket (1) and is used for positioning the leading edge I-beam of the engine nacelle; the reinforcement box positioning mechanism is arranged at the upper end of the tooling support bracket (1) and is used for positioning and supporting the reinforcement box (20) of the engine nacelle; the suspension point support box positioning mechanism is arranged at the upper end of the tooling support bracket (1) and is used for positioning and supporting the suspension point support box (18) of the engine and positioning the suspension point connecting piece (19) of the engine; the trailing edge beam positioning mechanism is arranged at the upper end of the tooling support bracket (1) and is used for positioning the trailing edge beam of the engine nacelle; the rib plate positioning mechanism is arranged at the upper end of the tooling support bracket (1) and is used for positioning the rib plate (21) of the engine nacelle; the skin positioning mechanism is arranged at the upper end of the tooling support bracket (1) and is used for positioning and supporting the skin (22) of the engine nacelle.

2. The aircraft engine nacelle assembly tooling according to claim 1, characterized in that, The joint positioning mechanism includes two joint positioning components. The two joint positioning components are respectively arranged on the left and right sides of the front part of the upper end of the tooling support bracket (1). The joint positioning component includes a joint support plate (2) and a joint positioning plate (3) which are connected to each other. The joint support plate (2) is an L-shaped plate. The horizontal part of the joint support plate (2) is connected to the tooling support bracket (1). The vertical part of the joint support plate (2) is connected to the joint positioning plate (3) through a pin. The joint positioning plate (3) is provided with a joint positioning hole, and the mounting joint (17) is provided with a joint limiting hole. A positioning bolt passes through the joint positioning hole and the joint limiting hole, and a nut is screwed onto the positioning bolt to fix the mounting joint (17) on the joint positioning plate (3).

3. The aircraft engine nacelle assembly tooling according to claim 1, characterized in that, The leading edge beam positioning mechanism includes a leading edge beam middle positioning component and two leading edge beam end positioning components; The leading edge beam middle positioning component is arranged at the middle position of the front side of the upper end of the tooling support bracket (1). The leading edge beam middle positioning component includes a leading edge beam middle support plate (4) and a leading edge beam middle positioning plate (5) which are connected to each other. The leading edge beam middle support plate (4) is an L-shaped plate. The horizontal part of the leading edge beam middle support plate (4) is connected to the tooling support bracket (1). The vertical part of the leading edge beam middle support plate (4) is connected to the leading edge beam middle positioning plate (5) through a pin. The leading edge beam middle positioning plate (5) is provided with a leading edge beam middle positioning hole, and the leading edge I-beam is provided with a leading edge beam middle limiting hole. A positioning bolt passes through the leading edge beam middle positioning hole and the leading edge beam middle limiting hole, and a nut is screwed onto the positioning bolt to fix the leading edge I-beam on the leading edge beam middle positioning plate (5); The two leading edge beam end positioning assemblies are respectively arranged on the left and right sides of the upper end of the tooling bracket (1), and are arranged on the inner side of the skin positioning mechanism. The leading edge beam end positioning assemblies include a leading edge beam end support plate (6) and a leading edge beam end positioning plate (7) which are connected to each other. The leading edge beam end support plate (6) is an L-shaped plate. The horizontal portion of the leading edge beam end support plate (6) is connected to the tooling bracket (1). The vertical portion of the leading edge beam end support plate (6) is connected to the leading edge beam end positioning plate (7) through a latch. The leading edge beam end positioning plate (7) is provided with a leading edge beam end positioning hole. The leading edge I-beam is provided with a leading edge beam end limiting hole. The positioning bolt passes through the leading edge beam end positioning hole and the leading edge beam end limiting hole. The nut is screwed onto the positioning bolt to fix the leading edge I-beam on the leading edge beam end positioning plate (7).

4. The aircraft engine nacelle assembly tooling according to claim 3, characterized in that, The reinforcement box positioning mechanism is arranged between the two front edge beam end positioning components, and the reinforcement box positioning mechanism comprises two reinforcement box support plates (10) and a reinforcement box positioning plate (11). The two reinforcement box support plates (10) are respectively arranged on the left and right sides below the reinforcement box positioning plate (11). The reinforcement box support plate (10) is an L-shaped plate. The horizontal part of the reinforcement box support plate (10) is connected to the tooling bracket (1), and the vertical part of the reinforcement box support plate (10) is connected to the reinforcement box positioning plate (11). The reinforcement box positioning plate (11) is provided with a reinforcement box positioning hole, and the reinforcement box (20) is provided with a reinforcement box limiting hole. The positioning bolt passes through the reinforcement box positioning hole and the reinforcement box limiting hole, and the nut is screwed on the positioning bolt to fix the upper reinforcement box (20) on the reinforcement box positioning plate (11).

5. The aircraft engine nacelle assembly tooling according to claim 4, characterized in that, The upper surface of the reinforcement box positioning plate (11) is an inclined surface that matches the lower surface of the reinforcement box (20).

6. The aircraft engine nacelle assembly tooling according to claim 1, characterized in that, The suspension point support box positioning mechanism comprises two suspension point support box positioning assemblies, which are respectively arranged on the left and right sides of the middle of the upper end of the tooling bracket (1) and arranged on the inner side of the skin positioning mechanism, and the suspension point support box positioning assembly comprises a suspension point support box support plate (8) and a suspension point support box positioning plate (9) which are connected to each other, and the suspension point support box support plate (8) is an L-shaped plate, the horizontal part of the suspension point support box support plate (8) is connected to the tooling bracket (1), and the vertical part of the suspension point support box support plate (8) is connected to the suspension point support box positioning plate (9). The lifting point support box positioning plate (9) is provided with a lifting point support box positioning hole and a connecting piece positioning hole, the lifting point support box (18) is provided with a lifting point support box limiting hole, the positioning bolt passes through the lifting point support box positioning hole and the lifting point support box limiting hole, the nut is screwed on the positioning bolt to fix the lifting point support box (18) on the lifting point support box positioning plate (9), the lifting point connecting piece (19) is provided with a connecting piece limiting hole, the positioning bolt passes through the connecting piece positioning hole and the connecting piece limiting hole, the nut is screwed on the positioning bolt to fix the lifting point connecting piece (19) on the lifting point support box positioning plate (9).

7. A short nacelle assembly tooling for an aircraft engine according to claim 6, characterized in that, The upper surface of the suspension point support box positioning plate (9) is an inclined surface that fits the suspension point support box (18).

8. The assembly tooling for an aircraft engine nacelle according to claim 1, wherein, The trailing edge beam positioning mechanism includes two trailing edge beam positioning components, which are respectively arranged on the left and right sides of the rear part of the upper end of the tooling bracket (1), and are arranged inside the skin positioning mechanism. The trailing edge beam positioning component includes a trailing edge beam support plate (12) and a trailing edge beam positioning plate (13) that are connected to each other. The trailing edge beam support plate (12) is an L-shaped plate. The horizontal part of the trailing edge beam support plate (12) is connected to the tooling bracket (1), and the vertical part of the trailing edge beam support plate (12) is connected to the trailing edge beam positioning plate (13). The trailing edge beam positioning plate (13) is provided with a trailing edge beam positioning hole, and the trailing edge beam is provided with a trailing edge beam limiting hole. A positioning bolt passes through the trailing edge beam positioning hole and the trailing edge beam limiting hole, and a nut is screwed onto the positioning bolt to fix the trailing edge beam on the trailing edge beam positioning plate (13).

9. The aircraft engine nacelle assembly tooling according to claim 1, characterized in that, The rib positioning mechanism includes four rib positioning components, which are respectively arranged on the left and right sides of the upper end of the tooling bracket (1). The rib positioning component includes a rib support plate (14) and a rib positioning plate (15). The rib support plate (14) is an L-shaped plate. The horizontal part of the rib support plate (14) is connected to the tooling bracket (1), and the vertical part of the rib support plate (14) is connected to the rib positioning plate (15) through a pin. The rib positioning plate (15) is provided with a rib positioning hole, and the rib (21) is provided with a rib limiting hole. A positioning bolt passes through the rib positioning hole and the rib limiting hole, and a nut is screwed onto the positioning bolt to fix the rib (21) on the rib positioning plate (15).

10. The aircraft engine nacelle assembly tooling according to claim 9, characterized in that, The skin positioning mechanism includes two skin positioning plates (16), which are respectively arranged on the left and right sides of the upper end of the tooling bracket (1). The left and right ends of the skin positioning plate (16) are respectively connected to the rib positioning plate (15). The upper surface of the skin positioning plate (16) is an arc surface that fits the bottom of the skin (22).

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